This study was done to investigate the effect of perturbations of both oblate massive primaries on the periodic orbit-attitude behavior of satellites at the three-body problem. Governing equations of the perturbed coupled orbit-attitude were derived using principles of the Lagrangian mechanics. As initial conditions of the coupled model play a key role in finding periodic responses of both orbit and attitude, so the perturbed circular restricted three-body problem (P-CR3BP) coupled orbit-attitude correction algorithm was proposed to correct the initial guess of the coupled model. The correction algorithm requires an appropriate initial guess vector as the number of periodic solutions is limited. This initial guess vector consists of two parts: orbital and attitude dynamic state parameters. A suitable initial guess was suggested for orbital parameters considering a small error at the initial conditions of the unperturbed periodic orbits. These initial conditions were extracted by another orbital correction algorithm to correct orbital states of periodic orbits in the unperturbed circular restricted three-body problem (U-CR3BP). Furthermore, the initial guess of attitude dynamic parameters was identified by the Poincaré mapping method. Considering oblate perturbations would change the initial conditions of periodic orbits at P-CR3BP relative to U-CR3BP. Also, because the proposed model of the coupled orbit-attitude governing equations is such that only orbital state parameters influence attitude dynamic parameters, so the behavior of attitude dynamics will also change by altering orbital motion. Comparison of patterns in Poincaré maps, satellites angular velocity, and initial conditions of periodic coupled orbit-attitude response in U-CR3BP and P-CR3BP indicated the effect of both oblate primaries perturbations. Consideration of these perturbations resulted in a more accurate simulation of the study environment that helps to understand the natural motion of the satellite.

本研究的目的是研究两个扁大质量原色的扰动对卫星在三体问题上的周期轨道姿态行为的影响。使用拉格朗日力学原理推导出了扰动耦合轨道-姿态的控制方程。由于耦合模型的初始条件在寻找轨道和姿态的周期响应中起着关键作用，因此提出了扰动圆限制三体问题（P-CR3BP）耦合轨道姿态修正算法来修正初始猜测的轨道姿态。耦合模型。由于周期解的数量有限，修正算法需要一个合适的初始猜测向量。这个初始猜测向量由两部分组成：轨道和姿态动态参数。考虑到未扰动周期轨道初始条件下的小误差，建议对轨道参数进行合适的初始猜测。这些初始条件是通过另一种轨道校正算法提取的，以校正未受扰动圆形受限三体问题（U-CR3BP）中周期轨道的轨道状态。此外，姿态动力学参数的初始猜测是通过庞加莱映射方法识别的。考虑到扁球扰动会改变 P-CR3BP 相对于 U-CR3BP 的周期轨道的初始条件。此外，由于提出的轨道-姿态耦合控制方程模型是只有轨道状态参数影响姿态动力学参数，所以姿态动力学的行为也会随着轨道运动的改变而改变。庞加莱地图中的模式、卫星角速度和 U-CR3BP 和 P-CR3BP 中周期性耦合轨道-姿态响应的初始条件的比较表明了两种扁圆原色扰动的影响。考虑到这些扰动，可以更准确地模拟研究环境，有助于了解卫星的自然运动。